Combined flight recorder and aircraft

Abstract

The utility model discloses a combined aviation recording device and aircraft, including shell body, data acquisition and processing module, data storage module and independent power supply unit, the shell body inside is divided into two independent flight data record cabin and cabin sound record cabin through the spacer support, data acquisition and processing module set up in the flight data record cabin, is used for gathering and preprocessing the flight data from the sensor of aircraft, data storage module includes first storage unit and second storage unit, first storage unit sets up in the flight data record cabin, and data acquisition and processing module electric connection, second storage unit sets up in the cabin sound record cabin, the external interface of flight data record cabin and cabin sound record cabin is integrated on the shared multifunctional interface board, and the multifunctional interface board sets up on the lateral wall of shell body, the utility model discloses compact structure, saves space and material cost, and the installation and maintenance of being convenient for, high stability.

Description

Technical Field

[0001] This utility model relates to the field of avionics technology, and in particular to a combined flight recording device and aircraft. Background Technology

[0002] In current technology, modern aircraft are generally equipped with a Flight Data Recorder (FDR) for recording flight data and a Cockpit Voice Recorder (CVR) for recording cockpit voice, commonly known as a "black box." Currently, the FDR and CVR are usually installed as two separate devices in different parts of the aircraft, each occupying space, requiring cabling, and connected to a power source. This separate design suffers from problems such as complex installation structure, large space occupation, heavy overall weight, and inconvenient maintenance. For small unmanned aerial vehicles (UAVs) and general aviation aircraft, which are sensitive to space and weight, the burden of two separate devices is particularly pronounced. Utility Model Content

[0003] The technical problem to be solved by this utility model is to overcome the shortcomings of the prior art and provide a combined flight recording device and aircraft with a compact structure, saving space and material costs, easy installation and maintenance, and high stability.

[0004] To solve the above-mentioned technical problems, the technical solution of this utility model is as follows: A combined flight recording device includes a housing, a data acquisition and processing module, a data storage module, and an independent power supply unit; The interior of the outer shell is divided into two independent flight data recording compartments and cabin voice recording compartments by a partition bracket; The data acquisition and processing module is located in the flight data recording cabin and is used to collect and preprocess flight data from various sensors of the aircraft. The data storage module includes a first storage unit and a second storage unit; The first storage unit is located inside the flight data recording cabin and is electrically connected to the data acquisition and processing module for storing flight data; The second storage unit is located inside the cockpit voice recording compartment and is used to store voice data from the cockpit audio control unit; The external interfaces of the flight data recording cabin and the cabin voice recording cabin are integrated on a shared multi-functional interface board, which is located on the side wall of the outer shell.

[0005] Furthermore, the isolation bracket is made of ceramic.

[0006] Furthermore, an underwater positioning beacon is also provided on the outside of the outer shell.

[0007] Furthermore, both the flight data recording cabin and the cabin voice recording cabin are equipped with protective covers, and the first storage unit and the second storage unit are both located inside the protective covers.

[0008] Furthermore, a cushioning pad is provided on the inner wall of the protective cover.

[0009] Furthermore, the independent power supply unit is a built-in battery used to provide emergency power for the entire device.

[0010] Furthermore, a positioning post is also provided on the outer side of the outer shell.

[0011] Furthermore, the outer shell is made of an alloy material.

[0012] This utility model also provides an aircraft that includes the above-described combined flight recording device.

[0013] Furthermore, the combined flight recorder is installed on the aircraft's electronic equipment rack.

[0014] By adopting the above technical solution, this utility model has the following beneficial effects: 1. This utility model integrates the functional units of FDR and CVR into a single housing and adopts a physically isolated compartment design, which greatly reduces the overall volume and installation space occupied. It is particularly suitable for aircraft with limited space, and is highly integrated and space-saving.

[0015] 2. By sharing a single outer shell, interface plate, and some structural components, this utility model reduces redundant structures and effectively lowers the total weight of the equipment.

[0016] 3. This utility model requires only one installation position, one set of cable wiring and one power interface, which simplifies the installation process during aircraft final assembly and also facilitates daily inspection and maintenance by ground staff.

[0017] 4. The internal physical isolation design of this utility model ensures that even if one functional unit fails, such as by catching fire, it will not easily affect another functional unit, thus guaranteeing the relative security of the data.

[0018] 5. This utility model, through the design of an internal protective cover and a buffer pad, can effectively protect the first and second storage units and prevent them from being damaged further.

[0019] The above description is merely an overview of the technical solutions of the embodiments of this application. In order to better understand the technical means of the embodiments of this application and to implement them in accordance with the contents of the specification, and to make the above and other objects, features and advantages of the embodiments of this application more obvious and understandable, specific implementation methods of this application are described below. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of an embodiment of the present utility model; Figure 2 This is a schematic diagram of the internal structure of an embodiment of the present utility model; Figure 3 This is a partial structural schematic diagram of an embodiment of the present utility model.

[0021] The attached figures are labeled as follows: 1. Outer shell; 2. Underwater positioning beacon; 3. Multifunctional interface board; 4. Isolation bracket; 5. Flight data recording cabin; 6. Cabin voice recording cabin; 7. Data acquisition and processing module; 8. First storage unit; 9. Second storage unit; 10. Independent power supply unit; 11. Protective cover; 12. Positioning post. Detailed Implementation

[0022] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0023] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains; the terminology used herein in the specification of the application is for the purpose of describing particular embodiments only and is not intended to limit the application; the terms “comprising” and “having”, and any variations thereof, in the specification, claims and drawings of this application are intended to cover non-exclusive inclusion.

[0024] The term "embodiment" as used herein means that a particular feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of the phrase "embodiment" in various places throughout the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described herein can be combined with other embodiments.

[0025] Furthermore, the terms "first," "second," etc., in the specification and claims of this application or in the aforementioned drawings are used to distinguish different objects rather than to describe a specific order, and may explicitly or implicitly include one or more of the features.

[0026] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, "connection" or "joining" in mechanical structures can refer to a physical connection, such as a fixed connection, for example, a connection fixed by fasteners, such as a connection fixed by screws, bolts, or other fasteners; a physical connection can also be a detachable connection, such as a snap-fit ​​or interlocking connection; a physical connection can also be an integral connection, such as a connection formed by welding, bonding, or integral molding. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0027] To make the contents of this utility model easier to understand, the present utility model will be further described in detail below with reference to specific embodiments and accompanying drawings.

[0028] Please see Figure 1 , Figure 2 and Figure 3 In this embodiment, a combined flight recording device is provided, mainly composed of a housing 1, a data acquisition and processing module 7, a data storage module, and an independent power supply unit 10. The housing 1 is internally divided into two independent sealed compartments by an isolation bracket 4: a flight data recording compartment 5 and a cabin voice recording compartment 6. The isolation bracket 4 is made of ceramic, and the use of fire-resistant and heat-insulating ceramic materials prevents a fire or high-temperature malfunction in one compartment from affecting the other, thus meeting the safety requirements for the recording device in airworthiness regulations.

[0029] Specifically, the data acquisition and processing module 7 is located within the flight data recording bay 5 and is used to acquire and preprocess flight data from various aircraft sensors. The data storage module includes a first storage unit 8, i.e., the FDR memory, and a second storage unit 9, i.e., the CVR memory. The data acquisition and processing module 7 receives various parameters from the aircraft data bus, such as altitude, airspeed, attitude, and engine parameters, through the multi-function interface board 3, performs preprocessing, and writes them into the first storage unit 8 for storage. The first storage unit 8 is located within the flight data recording bay 5 and is electrically connected to the data acquisition and processing module 7 for storing flight data. The second storage unit 9 is located within the cockpit voice recording bay 6 and is used to store voice data from the cockpit audio control unit. It also receives audio signals from the cockpit microphone through the multi-function interface board 3 and stores them directly. In this way, the functional units of the FDR and CVR, i.e., the flight data recording bay 5 and the cockpit voice recording bay 6, are integrated into a single outer shell 1, and a physical isolation compartment, i.e., an isolation bracket 4, is used, which greatly reduces the overall volume and installation space occupied. This is particularly suitable for aircraft with limited space, achieving high integration and saving space. Although they share a single enclosure, the two storage units and their associated circuitry are physically isolated, ensuring compliance with the security requirements that FDR and CVR must be independent and not interfere with each other.

[0030] To further save space and reduce material costs, the external interfaces of the flight data recording cabin 5 and the cabin voice recording cabin 6 in this embodiment are integrated onto a shared multi-functional interface board 3, which is located on the side wall of the outer shell 1. The multi-functional interface board 3 can be integrally molded or fixed by welding, riveting, or other methods. By sharing a single outer shell 1, interface board, and some structural components, redundant structures are reduced, effectively lowering the overall weight of the equipment. After installation, it can be directly connected to external plug-ins.

[0031] To facilitate subsequent positioning, an underwater positioning beacon 2 is also provided on the exterior of the outer casing 1 in this embodiment. The underwater positioning beacon 2 can be protected by the outer casing.

[0032] To ensure the security of the internally stored information, protective covers 11 are provided in both the flight data recording bay 5 and the cabin voice recording bay 6 in this embodiment. The protective covers 11 are made of materials with strong shock resistance and good high-temperature insulation performance. The first storage unit 8 and the second storage unit 9 are both located inside the protective covers 11. To reduce the impact on the first storage unit 8 and the second storage unit 9, a cushioning pad is provided on the inner wall of the protective covers 11 in this embodiment.

[0033] Meanwhile, the independent power supply unit 10 in this embodiment is a built-in battery, which is used to provide emergency power for the entire device, ensuring that it can still work for a short time after the aircraft's main power fails, ensuring safety and reliability, and guaranteeing the retention of information and data.

[0034] Of course, for ease of installation and positioning, a positioning post 12 is also provided on the outer side of the outer shell 1 in this embodiment to facilitate stable and secure installation and fixing. For impact resistance and heat insulation protection, the outer shell 1 in this embodiment is made of alloy material, which is a metal composite material that is resistant to high impact and high temperature.

[0035] In addition, this embodiment also provides an aircraft in which the above-mentioned combined flight recording device is installed on its tail or other airworthiness certification-permitted parts, which of course also has all the above advantages and benefits.

[0036] As can be seen from the above design, this embodiment requires only one installation position, one set of cabling, and one power interface, simplifying the installation process during aircraft final assembly and facilitating routine inspections and maintenance by ground staff. Simultaneously, the internal physical isolation design ensures that even if one functional unit malfunctions, such as in the event of a fire, it will not easily affect another functional unit, guaranteeing relative data security. Furthermore, the internal protective cover 11 and buffer pad design effectively protect the first storage unit 8 and the second storage unit 9, preventing them from suffering greater damage.

[0037] In the description of this specification, references to terms such as "an embodiment," "example," "specific example," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0038] The above specific embodiments further illustrate the technical problems, technical solutions, and beneficial effects of this utility model. It should be understood that the above descriptions are merely specific embodiments of this utility model and are not intended to limit this utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A combined flight recording device, characterized in that: It includes an outer casing (1), a data acquisition and processing module (7), a data storage module, and an independent power supply unit (10). The outer shell (1) is divided into two independent flight data recording compartments (5) and cabin voice recording compartments (6) by an isolation bracket (4). The data acquisition and processing module (7) is located in the flight data recording cabin (5) and is used to collect and preprocess flight data from various sensors of the aircraft. The data storage module includes a first storage unit (8) and a second storage unit (9); The first storage unit (8) is located inside the flight data recording cabin (5) and is electrically connected to the data acquisition and processing module (7) for storing flight data; The second storage unit (9) is located in the cockpit voice recording compartment (6) and is used to store voice data from the cockpit audio control unit; The external interfaces of the flight data recording cabin (5) and the cabin voice recording cabin (6) are integrated on a shared multi-functional interface board (3), which is located on the side wall of the outer shell (1).

2. The combined flight recording device according to claim 1, characterized in that: The isolation bracket (4) is made of ceramic.

3. The combined flight recording device according to claim 1, characterized in that: An underwater positioning beacon (2) is also provided on the outside of the outer shell (1).

4. The combined flight recording device according to claim 1, characterized in that: The flight data recording cabin (5) and the cabin voice recording cabin (6) are both equipped with protective covers (11), and the first storage unit (8) and the second storage unit (9) are both located inside the protective covers (11).

5. A combined flight recording device according to claim 4, characterized in that: A buffer pad is provided on the inner wall of the protective cover (11).

6. A combined flight recording device according to claim 1, characterized in that: The independent power supply unit (10) is a built-in battery used to provide emergency power for the entire device.

7. A combined flight recording device according to claim 1, characterized in that: A positioning post (12) is also provided on the outside of the outer shell (1).

8. A combined flight recording device according to claim 1, characterized in that: The outer shell (1) is made of alloy material.

9. An aircraft, characterized in that: Includes the combined flight recording device as described in any one of claims 1-8.

10. An aircraft according to claim 9, characterized in that: The combined flight recorder is installed on the aircraft's electronic equipment rack.

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